Integrated antenna system for imaging microsatellites

ABSTRACT

Examples of imaging microsatellites are described that have an imaging system and antenna system disposed within the microsatellite body when the microsatellite is in a non-deployed state. The properties of the antenna system can be adjusted such that the antenna system does not impact, contact, or displace the imaging system when the microsatellite is in the non-deployed state. The properties of the antenna system can be adjusted such that the antenna system does not contact or impact the body of the microsatellite or any other structure when the microsatellite transitions to a deployed state. The antenna system can be configured to achieve a desired gain and/or data transmission rate by adjusting properties of the antenna system based on the radiation pattern of an antenna feed and geometric constraints imposed by the imaging system. Examples of methods for designing such imaging microsatellites are provided.

CROSS-REFERENCE TO RELATED APPLICATIONS

This application is a continuation of U.S. patent application Ser. No.13/935,770, filed Jul. 5, 2013, entitled “INTEGRATED ANTENNA SYSTEM FORIMAGING MICROSATELLITES,” which is a continuation of U.S. patentapplication Ser. No. 13/326,175, filed Dec. 14, 2011, now U.S. Pat. No.8,531,524, entitled “INTEGRATED ANTENNA SYSTEM FOR IMAGINGMICROSATELLITES,” which claims the benefit of priority under 35 U.S.C.§119(e) of U.S. Provisional Patent Application 61/423,473, filed Dec.15, 2010, entitled “INTEGRATED REFLECTOR ANTENNA AND OPTICAL SEAL FORMICRO IMAGING SATELLITES.” U.S. patent application Ser. No. 13/935,770,is also a continuation of U.S. patent application Ser. No. 13/566,548,filed Aug. 3, 2012, now U.S. Pat. No. 8,482,610, entitled “INTEGRATEDANTENNA SYSTEM FOR IMAGING MICROSATELLITES,” which is a continuation ofInternational Application No. PCT/US2011/064998, designating the UnitedStates, with an international filing date of Dec. 14, 2011, titled“INTEGRATED ANTENNA SYSTEM FOR IMAGING MICROSATELLITES,” which claimsthe benefit under 35 U.S.C. §119(e) of U.S. Provisional PatentApplication No. 61/423,473, filed Dec. 15, 2010, titled “INTEGRATEDREFLECTOR ANTENNA AND OPTICAL SEAL FOR MICRO IMAGING SATELLITES.” Eachof the foregoing patent applications and patents is hereby incorporatedby reference herein in its entirety for all each application or patentdiscloses, and each application and patent is made a part of thisspecification as if set forth fully herein.

BACKGROUND

1. Field

The disclosure generally relates to microsatellites, and moreparticularly, to antenna systems and imaging systems formicrosatellites.

2. Description of the Related Art

Microsatellites are satellites that are smaller than traditionalsatellites. Due to their smaller size, microsatellites generally costless to build and deploy into orbit above the Earth. As a result,microsatellites present opportunities for educational institutions,governments, and commercial entities to launch and deploymicrosatellites for a variety of purposes with fewer costs compared totraditional, large satellites. Microsatellites have been deployed forpurposes such as data collection for scientific experiments, providingcommunication links, and imaging the Earth.

SUMMARY

The systems, methods and devices of the disclosure each have severalinnovative aspects, no single one of which is solely responsible for thedesirable attributes disclosed herein. Without limiting the scope of theclaims, some of the advantageous features will now be summarized.

Certain challenges are presented when designing microsatellites such asincorporating the desired structure and electronics into a relativelysmall form factor, maximizing the efficiency of the included componentsgiven volume and mass constraints, and providing sufficientcommunication systems to relay information to and from ground-basedsystems. Imaging microsatellites, for example, utilize much of thevolume of the satellite for the imaging system, reducing the availablespace for other components, such as antennas for communication. Inaddition, imaging microsatellites can produce relatively large amountsof information making it desirable to incorporate a communication systemcapable of a relatively high data transmission rate, consequently makinglarger antenna systems more desirable.

Microsatellites can be advantageous where satellite capabilities aredesirable but the cost to manufacture and launch a traditional, largesatellite renders the possibility impracticable or unworkable.Microsatellites are smaller and weigh less than traditional, largesatellites and therefore are generally cheaper to manufacture and putinto orbit. However, challenges arise when reducing the size ofcomponents and systems to fit into a microsatellite. For instance, largesatellites may include large communications antennas making high datatransmission rates possible. Microsatellites, on the other hand, arelimited in the size of antenna that may be included, possibly reducingthe data transmission rate available. The gain of the antenna may alsobe affected by the size of the antenna, affecting the link margin andsize of ground communication systems. The gain of the antenna may alsobe affected by the frequency band of communication with the ground orother satellites. Imaging microsatellites also incorporate imagingsystems, reducing the space available for antenna systems. Certainantenna systems may satisfy space and weight concerns yet createadditional costs and introduce undesirable complexity into the system.In imaging microsatellites, the imaging system generally has a desiredconfiguration which limits the configuration of other systems andcomponents within the satellite. For example, it may be desirable thatthe imaging system have a field of view unobstructed by other componentswhen the satellite is deployed. The antenna configuration, then, can beadvantageously configured to fit within the body of the microsatellitewithout disturbing the imaging system configuration. In someembodiments, an imaging microsatellite can be configured to house bothan antenna system and an imaging system, communicate with a data ratesufficient to transmit image and video data to a ground-basedcommunication system, reduce system complexity, reduce manufacturecosts, optimize the antenna system given the size and/or massconstraints, and/or increase the packing efficiency of both antenna andimaging system.

Some embodiments provide an imaging microsatellite having an antennasystem and an imaging system. The microsatellite can include a body aplurality of surfaces forming an interior cavity and an opening in thebody. The imaging system can be disposed within the interior cavity ofthe microsatellite and configured to image a field of view through theopening in the microsatellite body. The microsatellite can include adoor and the antenna system can be coupled to the door.

The antenna system can include an antenna reflector coupled to the door,an antenna feed support attached to the antenna reflector or the door,and an antenna feed attached to the antenna feed support. The antennafeed support can be configured to secure the antenna feed in a fixedposition relative to the antenna reflector.

The door can be movable from a closed position to an open position,wherein in the closed position the door covers the opening and in theopen position the door uncovers the opening. The antenna system can beconfigured to fit within the interior cavity without coming into contactwith the imaging system when the door is in a closed position. Theantenna system can be configured to move with the door through theopening in an unobstructed manner when the door moves from the closedposition to the open position.

In some embodiments, the microsatellite can have a volume that is lessthan or equal to about 125 cm by 125 cm by 175 cm or a mass that is lessthan or equal to about 500 kg. The microsatellite can be configured tolaunch as a secondary payload on a launch vehicle configured to launch aprimary payload.

In some embodiments, the antenna reflector of the microsatellite canhave a diameter that is less than or equal to about 120 cm or greaterthan or equal to about 30 cm. The antenna reflector can have a diameterthat is greater than or equal to 50% of the width of the door or lessthan or equal to 98% of the width of the door. The antenna system can beconfigured to provide a gain greater than or equal to 25 dBi (e.g., dBisotropic, which measures antenna gain compared to a hypotheticalisotropic antenna) or a data transmission rate between about 1 Mbit/s to100 Mbit/s.

The imaging system can include a telescope. The imaging system telescopecan include a primary minor, a secondary mirror, and a secondary minorsupport configured to secure the secondary mirror in a fixed positionrelative to the primary minor. For example, the imaging system telescopemay be a Cassegrain telescope or a Ritchey-Chrétien telescope. Theantenna feed can be disposed between the primary mirror and thesecondary mirror when the door is in the closed position. The imagingsystem can include a primary baffle associated with the primary minorand a secondary baffle associated with the secondary mirror. The antennafeed can be disposed between the primary baffle and the secondary bafflewhen the door is in the closed position.

Some embodiments provide for a method of designing an imagingmicrosatellite. The imaging microsatellite can include an interiorcavity and an opening. The microsatellite can include a door configuredto cover the opening when the microsatellite is in a non-deployed stateand to uncover the opening when the microsatellite is in a deployedstate. The microsatellite can include an antenna system attached to thedoor. The antenna system can include a reflector and an antenna feed.The microsatellite can include an imaging system disposed within theinterior cavity and configured to image a field of view through theopening when the microsatellite is in the deployed state.

The method of designing the imaging microsatellite includes obtainingconfiguration parameters for the microsatellite. The microsatelliteconfiguration parameters can include dimensions of the microsatellite.

The method can include obtaining configuration parameters for theimaging system. The imaging system configuration parameters can includedimensions and layout of the imaging system within the interior cavityof the microsatellite.

The method can include determining a layout of the antenna system suchthat (1) the antenna system does not contact or displace portions of theimaging system when the microsatellite is in the non-deployed state, and(2) the antenna system does not contact portions of the microsatellitewhen the microsatellite transitions from the non-deployed to thedeployed state.

The method can include adjusting properties of the antenna system suchthat the reflector matches a radiation pattern of the antenna feed and adesired antenna gain or data transmission rate is achieved.

In some embodiments, adjusting the properties of the antenna system caninclude adjusting at least one of a diameter, a depth, or a focal lengthof the reflector. The steps of determining and adjusting can be repeateduntil a ratio of the focal length to the diameter is in a desired range.In various implementations, the desired data transmission rate can begreater than or equal to about 1 Mbit/s, greater than or equal to about10 Mbit/s, greater than or equal to about 50 Mbit/s, greater than orequal to about 75 Mbit/s, or greater than or equal to about 100 Mbit/s.In various implementations, the desired data transmission rate can be ina range between about 1 Mbit/s and 100 Mbit/s, in a range between about10 Mbit/s and 80 Mbit/s, or in some other range. In variousimplementations, the desired antenna gain can be greater than or equalto about 15 dBi, greater than or equal to about 20 dBi, greater than orequal to about 25 dBi, or greater than or equal to about 30 dBi. Invarious implementations, the desired antenna gain can be in a rangebetween about 10 dBi and 30 dBi, between about 15 dBi and 25 dBi,between about 20 dBi and 30 dBi, between about 25 dBi and 30 dBi,between about 28 dBi and 29 dBi, or some other range.

Some embodiments provide for an imaging microsatellite that can includea body that can have a volume envelope less than about 125 cm by 125 cmby 175 cm or a mass envelope less than about 500 kg. The body can havean interior cavity and an opening in the body. The microsatellite caninclude an imaging system disposed within the interior cavity. Theimaging system can include a primary minor and a secondary mirror. Themicrosatellite can include a door attached to the body. Themicrosatellite can have a non-deployed state in which the opening iscovered by the door, and a deployed state in which the opening isunobstructed by the door and the imaging system can image a field ofview through the opening. The microsatellite can include an antennasystem. The antenna system can have a reflector and a feed, and theantenna system can be coupled to the door. When the microsatellite is inthe non-deployed state, the feed can be disposed between the primaryminor and the secondary minor. The antenna system can be configured tomove through the opening without contacting portions of the imagingsystem or portions of the body of the microsatellite when themicrosatellite transitions from the non-deployed state to the deployedstate.

In some embodiments, the imaging system can include a primary baffleassociated with the primary mirror and a secondary baffle associatedwith the secondary minor. The antenna feed can be disposed between theprimary baffle and the secondary baffle when the microsatellite is inthe non-deployed state. The primary mirror and the secondary minor canbe spaced apart by two or more support struts. The feed can be disposednear a focus of the reflector by a feed support, and the feed supportcan extend between two adjacent struts when the microsatellite is in thenon-deployed state.

In some embodiments, the antenna reflector can have a diameter d andfocal length f. The antenna reflector focal length, f, and diameter, d,can be adjusted to obtain a ratio f/d that matches a radiation patternof the feed.

BRIEF DESCRIPTION OF THE DRAWINGS

Throughout the drawings, reference numbers can be reused to indicategeneral correspondence between reference elements. The drawings areprovided to illustrate example embodiments described herein and are notintended to limit the scope of the disclosure.

FIG. 1 is a plan view of an example of an imaging system and antennasystem within a satellite body according to some embodiments of animaging microsatellite.

FIG. 2 is a plan view of an embodiment of an imaging microsatelliteafter an antenna system has been deployed.

FIG. 3 is a plan view of an embodiment of an imaging microsatellitebefore an antenna system has been deployed.

FIG. 4 is a schematic cross-section view that illustrates examples ofsome design considerations when combining an imaging system and antennasystem within a microsatellite.

FIG. 5 is a flow diagram representing an example of a method ofdeploying an integrated reflector antenna system in an imagingmicrosatellite.

FIG. 6 is a flow diagram representing an example of a method ofdesigning an imaging microsatellite with an integrated reflector antennasystem.

DETAILED DESCRIPTION

Unless explicitly indicated otherwise, terms as used herein will beunderstood to imply their customary and ordinary meaning. For example,microsatellite is a broad term and is to be given its ordinary andcustomary meaning to a person of ordinary skill in the art (e.g., it isnot to be limited to a special or customized meaning), and includes,without limitation, satellites with a mass less than or equal to about500 kg and/or physical dimensions less than or equal to about 125 cm×125cm×175 cm, or satellites that launch as a secondary payload on a launchvehicle. According to some conventions, satellites having a mass lessthan or equal to about 500 kg are classified as small satellites withfurther divisions being made based on their mass. For example, in oneclassification system, small satellites are deemed minisatellites whenthey have a mass between about 100 kg and 500 kg, microsatellites whenthey have a mass between about 10 kg and 100 kg, nanosatellites whenthey have a mass between about 1 kg and 10 kg, picosatellites when theyhave a mass between about 0.1 kg and 1 kg, and femtosatellites when theyhave a mass less than or equal to about 100 g. However, any reference tomicrosatellite, minisatellite, or small satellite in this disclosureshould be understood to mean the general class of satellites having amass less than or equal to about 500 kg and/or physical dimensions lessthan or equal to about 125 cm×125 cm×175 cm; and not to the morespecific classification of satellites identified herein or other similarclassification schemes.

Some microsatellites may conform to ESPA standards. ESPA stands for EELVSecondary Payload Adapter, and EELV stands for Evolved Expendable LaunchVehicle, which include, for example, Atlas V and Delta IV launchvehicles. ESPA specifications have been adopted by many in themicrosatellite industry as a guideline for determining acceptablemicrosatellite mass and/or volume for inclusion in launch vehicles. ESPAstandards recite a mass envelope of less than or equal to about 180 kgand a volume envelope less than 90 cm×70 cm×60 cm. A microsatelliteconforming to these specifications would be suitable for inclusion in alaunch vehicle employing an EELV secondary payload adapter. The ESPAstandard provides non-limiting examples of envelopes for whatconstitutes a microsatellite; however, microsatellites configuredaccording to other standards may be suitable for other launch vehicles.

Explanations of other terms used in the following detailed descriptionare provided in a separate section below.

General Overview

Microsatellites are limited in size due in part to launch vehicleconstraints, which consequently reduces the available size of thecomponents included thereon. The limited size of the antenna systemgenerally reduces the available gain of the satellite antenna. The gainof the satellite antenna can be related to the communication frequency,with the gain generally increasing with frequency. However, satellitesmay be confined within an allocated a range of communicationfrequencies. For example, in 47 C.F.R. §2.106 the Federal CommunicationsCommission (FCC) has allocated a band of frequencies between about 8.0GHz and 8.4 GHz for imaging satellite communications. Thus, thecommunication frequency may only be altered within a relatively narrowband, limiting the ability to increase the antenna gain by increasingthe communication frequency. The gain of the satellite antenna can berelated to the available RF link margin which drives the datatransmission rate. Increasing the gain by increasing the antenna size,power to the antenna, communication frequency, or any combination ofthese can increase the data transmission rate. It would be advantageous,then, for a microsatellite system to increase the gain of the antennasystem, and relatedly the data transmission rate, while maintaining thesize within a desired envelope and the communication frequency within anallocated band. Larger satellites generally do not encounter thisproblem because the larger size and mass limitations allow for largerantennas with sufficient gains and link margins to achieve relativelyhigh data transmission rates, even when confined to a band ofcommunication frequencies. For example, large satellites often make useof large aperture reflector antennas to transmit data. These samesolutions generally are not available for microsatellites due to thesize and mass constraints imposed.

To increase the utility of microsatellites, therefore, it would beadvantageous to incorporate a relatively high gain antenna into a smallform factor or envelope of the microsatellite. One such possiblesolution may be to incorporate patch antenna arrays to increase the gainof the satellite antenna. However, as the gain requirement increases,the cost and complexity of manufacturing a patch array that meets thegain requirement outpaces the cost and complexity of the remainder ofthe microsatellite. Therefore, it would be advantageous to provide arelatively low-cost and relatively straight-forward antenna system thatsatisfies the gain requirements of the microsatellite system.Microsatellites according to the embodiments described hereinadvantageously allow for the incorporation of a relatively large antennareflector while maintaining the imaging system footprint within themicrosatellite, increasing the available gain, link margin, and datatransmission rate of the antenna system.

Example System Overview

Some embodiments provide an imaging microsatellite that includes anintegrated reflector antenna system and an imaging system. Theintegrated reflector antenna system and imaging system can be configuredto fit within the body of the microsatellite when it is not deployed.The characteristics of the antenna system can be tuned to increase thegain of the antenna, and thereby increase the possible data transmissionrate, while still being configured to be disposed within themicrosatellite body along with the imaging system. In someimplementations, the antenna system may be fully enclosed within themicrosatellite prior to deployment of the antenna system.

In some embodiments the integrated reflector antenna system comprises aparaboloid reflector surface having an antenna feed supportsubstantially securing an antenna feed at the focal point of thereflector. The diameter and focal length of the antenna may be tuned toimprove or optimize the antenna gain and transmission rate. The rangesthrough which the diameter and focal length may be tuned can be limitedby the available space in the body of the microsatellite, the imagingsystem configuration, the method of deployment of the microsatellite,the envelope of the secondary payload, or any combination of these.

The imaging microsatellite can include an optical seal and a doorattached to the body of the microsatellite. The door can comprise anopening mechanism configured to attach the door to a surface of themicrosatellite and to provide an axis of rotation and/or an openingtorque. The imaging microsatellite can include an opening configured toallow radiation to enter the imaging system. The door can be configuredto cover the opening when in a closed state. The imaging microsatellitecan include an optical seal configured to be substantially in contactwith the door when in a closed state and configured to substantiallyprevent contaminating particulates from passing through the opening. Forexample, in some embodiments the optical seal comprises a pliable memberdisposed along the periphery of an opening, the optical seal beingconfigured to substantially seal the opening from the introduction ofcontaminants. The sealing occurs due to the contact between the opticalseal and the door when it is in a closed state. In some embodiments, theantenna reflector can be attached to an interior surface of the doorsuch that when the door is in a closed state the antenna reflector canbe disposed within the satellite body. For example, a paraboloidreflector antenna having an antenna feed support and antenna feed can beattached to the interior side of a hinged door and can be configured topass through an opening in the microsatellite body when the doortransitions from an open to a closed state.

The imaging system of the microsatellite can include optical elements,support structure, electrical systems, image sensors, radiation filters,baffles, or any combination of these. In some embodiments, the imagingsystem comprises a primary mirror and a secondary minor configured toproduce an image on an image sensor disposed behind the primary mirror.A secondary mirror support structure can secure the secondary mirror ata substantially fixed position relative to the primary minor. In someembodiments, the antenna feed is disposed between the primary andsecondary minors and does not contact, impact, or displace the secondarymirror support when the door is in a closed state.

FIG. 1 is a plan view of an example of an imaging system and antennasystem within a satellite body according to some embodiments of animaging microsatellite. In FIG. 1, an example of an imagingmicrosatellite 100 in a non-deployed state is shown. Three side panelsof the microsatellite 100 have been removed from this illustration toshow the configuration of certain components in the interior cavity ofthe microsatellite when it is in a non-deployed state. In someimplementations, the microsatellite 100 is a secondary payload on alaunch vehicle designed to launch a primary payload (e.g., a largesatellite). The microsatellite 100 can include an interface 111 adaptedto engage a structure (e.g., an ESPA secondary payload adaptor) that canbe connected to the primary payload, so that the microsatellite 100 canbe transported as a ride-along on the launch vehicle.

The imaging microsatellite 100 can comprise an antenna system 101. Theantenna system 101 can comprise an antenna feed 102 connected to anantenna feed support 104. The antenna feed support 104 can be attachedto an antenna reflector 106 or to an interior side of a door 108. Thedoor 108 can be attached to the microsatellite 100 with hinges 126.

The imaging microsatellite 100 can comprise an imaging system 110. Theimaging system 110 can comprise a primary mirror 112 and a first baffle114 configured to limit the amount of stray photons incident on animaging sensor (not shown). The imaging system 110 can comprise asecondary minor support 116 configured to secure a secondary minor 118in a fixed position relative to the primary minor 112. The imagingsystem 110 can comprise a second baffle 120 attached to or surroundingthe secondary minor 118 or the secondary minor support 116. The secondbaffle 120 can be configured to substantially reduce the amount of strayradiation incident on the secondary mirror 118 that may otherwise end upimpinging on the image sensor in the absence of the second baffle 120.

The imaging system 110 of the microsatellite 110 can comprise aCassegrain telescope. The primary minor 112 can be a paraboloid and thesecondary mirror 118 can be a hyperboloid. The imaging system cancomprise additional optical elements, such as, for example, lenses,diffraction gratings, minors, prisms, fiber optics, light guides, or anycombination of these. The primary and secondary minors 112 and 118 canbe disposed such that their vertices and focal points are disposedsubstantially along a line. In some embodiments, the orientation of theminors can be such that their focal points and vertices do notsubstantially fall along a single line. In some embodiments, the imagingsystem 110 can comprise a Ritchey-Chrétien telescope wherein the primaryand secondary mirrors 112 and 118 can be hyperboloids.

The antenna system 101 of the microsatellite 100 can be attached to aninterior side of the door 108 such that when the door is in a closedstate, the antenna system can be disposed within the interior of themicrosatellite 100. When the door 108 is in a closed state, the antennasystem 101 can be configured to not contact, impact, or displace theimaging system 110. The antenna feed 102 can be configured to bepositioned in a region between the first and second baffles 114 and 120when the microsatellite is in the non-deployed state. The antenna feedsupport 104 can be configured to be disposed between elements of thesecondary mirror support 116 so as to not contact, impact, or displaceit when the door 108 is in a closed state. The antenna system 101 can beconfigured to improve or optimize the size, gain, and/or transmissionrate by changing the diameter, focal length, and/or depth of the antennareflector 106 provided that the antenna reflector 106, the antenna feedsupport 104, and the antenna feed 102 do not contact, impact, ordisplace the imaging system 110 when the microsatellite 100 is notdeployed.

The secondary minor support 116 can comprise one or more supportelements configured to support the secondary mirror 118 relative to theprimary minor 112. For example, in some embodiments the secondary minorsupport 116 comprises four support members extending from the primarymirror 112 to the secondary mirror as shown in FIG. 1. The four supportmembers can be substantially equidistant from one another, or may benon-uniformly spaced. The antenna feed support 104 can be configured tobe disposed between the support members of the secondary minor support116 when the microsatellite is in a non-deployed state. In someembodiments, the secondary mirror support 116 comprises one or moresupport members configured to allow the antenna feed support 104 to bepositioned in such a fashion that it does not contact, impact, ordisplace the imaging system 110 or the support elements of the secondaryminor support 116 when the door 108 is closed.

The antenna feed 102 can be positioned between the first and secondbaffles 114 and 120 when the door 108 is in a closed state. In someembodiments, the antenna feed 102 can be disposed such that itintersects a line passing substantially through the centers of the firstand second baffles 114 and 120. In some embodiments, the antenna feed102 can be disposed in such a manner as to not intersect this line. Insome embodiments, the antenna feed can be disposed such that itintersects a line passing substantially through the vertices of theprimary and secondary minors 112 and 118. In some embodiments, theantenna feed 102 can be disposed in such a manner as to not intersectthis line.

The microsatellite 100 can comprise a body with multiple sides or faces.On at least one side, the microsatellite 100 can comprise a panel, dome,cap, or the like which can function as the door 108. The hinges 126 cancomprise any suitable type of hinge such as, for example, spring hinges,space hinges, or the like. The door 108 can be configured tosubstantially cover an entire side or face of the microsatellite body.The door 108 can comprise a substantially planar rigid structure, adome, a pyramid, or any other suitable configuration providing a surfaceto attach the antenna reflector 106. The door 108 can be substantiallysecured in a closed state utilizing a release mechanism 130. The releasemechanism 130 can utilize any appropriate method for securing the door108 in a closed state, including, for example, mechanical latch andspring systems, inductive systems, magnetic latch and switch systems,electromagnetic systems, or any combination of these. In some satellitesystems, the release mechanism 130 uses a frangible bolt and can bereleased by fracturing or melting the bolt.

Solar panels can be disposed on one or more sides or faces of themicrosatellite 100 and can provide power to electrical components in themicrosatellite. Electrical components and systems can be included in thebody of the microsatellite 100 and can be configured to control andcommunicate with any system of the microsatellite 100 and/or analyze andrecord any data from those systems. In some embodiments, a datacollection system can be connected to the antenna feed 102. Datacollected from the data feed can be routed to electronic systemsdisposed within the microsatellite interior cavity. For example, thedata can be routed via a wire or optical fiber from the antenna feed 102down the antenna feed support 104 and into the door 108 and then routedthrough a hinge 126. The data can be routed through a wire that extendsfrom the antenna feed 102 to the interior face of the door 108 andthrough the opening in the microsatellite.

Example of a Deployed Imaging Microsatellite

FIG. 2 is a plan view of an embodiment of the imaging microsatellite 100after the antenna system 101 has been deployed. The antenna system 101can be attached to the door 108 of the microsatellite 100 such that theantenna system 101 exits the interior cavity of the microsatellite 100when the door 108 opens. The antenna system 101 can be attached to thedoor 108 using any suitable means including, for example, fasteners,adhesives, clamps, clips, friction fitting, or any combination of these.

A proximal end of the antenna feed support 104 (e.g., the end nearestthe reflector 106) can be integrally formed with or attached to theantenna reflector 106 or the door 108 using any suitable means such asfasteners, adhesives, clamps, clips, friction fitting, or the like. Asshown in FIG. 2, the antenna feed support 104 can pass through theantenna reflector 106 and can be attached to the door 108. The antennafeed 102 can be disposed on a distal end of the antenna support 104(e.g., the end farthest from the reflector 106) and can be integrallyformed with the antenna feed support 104 or attached to the distal endusing, for example, fasteners, adhesives, clamps, clips, frictionfitting, or any combination of these. The antenna feed 102 can comprisea rigid member to support an active feed element. The antenna feed 102can comprise a feed horn, a dipole driven element, a waveguide, anorthomode transducer, a polarizer, and/or any combination of these. Theantenna reflector 106 can comprise a reflector surface having a vertex,diameter, and focal length. The antenna feed 102 can be disposedsubstantially at the focal point of the antenna reflector 106.

The imaging microsatellite 100 can include an opening configured toallow radiation to enter the imaging system 110. The opening can beconfigured to be of a sufficient size such that the antenna system 101can pass through the opening upon the door 108 opening or closing. Theopening can include an optical seal 128 along a perimeter of theopening. The optical seal 128 can be configured to create a seal withthe door 108 when the microsatellite is in the non-deployed state, suchthat contaminants are substantially unable to enter into the interiorcavity of the microsatellite 100. When the door 108 is in a closedstate, the door 108 and the optical seal 128 can be substantially incontact with one another such that a seal can be created.

The dimensions of the antenna reflector 108 can be configured tosubstantially occupy the available space on the door 108 of themicrosatellite 100. The aperture of the reflector antenna system 101 canbe related to the gain of the system and the data transmission rate.Therefore, it is desirable to substantially increase or maximize theaperture of the antenna reflector 106 given the size constraints of theenvelope, the size of the opening, and the dimensions of the door 108.In some embodiments, the antenna reflector 108 can be a paraboloidhaving a substantially circular cross-section. The aperture of theantenna reflector 108 in this configuration scales with the square ofthe diameter. The diameter of the antenna reflector 106 can be less thanor equal to about 120 cm, greater than or equal to about 30 cm, and/orbetween about 40 cm and 50 cm. The diameter of the antenna reflector 106can be related to the shorter of the length or width shortest dimensionof the door 108 and can be less than or equal to about 98% of that size,greater than or equal to about 50% of that size, between about 75% to98% of that size, between about 80% to 95% of that size, and/or betweenabout 90% to 95% of that size.

Example of an Imaging Microsatellite in a Non-Deployed State

FIG. 3 is a plan view of an embodiment of the imaging microsatellite 100before the antenna system has been deployed. The door 108 can beconfigured to substantially be in contact with the optical seal 128(see, e.g., FIG. 2) and a surface of the microsatellite 100 when in aclosed state. The optical seal can be configured to be in contact withthe door 108. When the door 108 is in the closed state, the releasemechanism 130 can apply a torque or force on the door 108 to prevent thehinges 126 from opening the door 108. In the closed state, there can bea substantial seal between the door 108 and the optical seal 128 toprevent entry of contaminants into the interior of the microsatellite100, which beneficially may decrease the likelihood of contamination ordamage to the imaging system or antenna system. When the microsatelliteis in a suitable orbit and attitude, the door 108 can be opened todeploy the antenna system 101 and to permit the imaging system 110 toimage targets on the Earth. In order to open the door 108, the releasemechanism 130 can be released, and the one or more hinges 126 can applya torque or force on the door 108 to rotate the door 108 into thedeployed state shown in FIG. 2.

As shown in FIG. 3, the microsatellite 100 can have a length L, a widthW, and a height H. In some implementations, each of L, W, and H is lessthan about 175 cm. As discussed herein, the size of the microsatellite(e.g., L, W, and H) can be selected so that the microsatellite isadapted to be a secondary payload on a launch vehicle. For example, thesize (and/or mass) of the microsatellite can be selected to conform toESPA guidelines.

The example microsatellite 100 illustrated in FIGS. 1-3 has six sidesbut in other implementations, the microsatellite may comprise anysuitable number of sides or faces and may be in any appropriateconfiguration, such as, for example, a cube, sphere, octagonal prism, orany polyhedron, or any three-dimensional structure with any number ofplanar and/or curved faces.

Examples of Factors for Improving or Optimizing the Antenna Design

FIG. 4 is a schematic cross-section view that illustrates examples ofsome design considerations when combining an imaging system 110 andantenna system 101 within a microsatellite 100. FIG. 4 shows examples ofvarious factors that can affect the gain and/or data transmission rateof the antenna system 101. In some implementations, the antennareflector 106 can have a diameter, d, a focal length, f, and a depth, h.In FIG. 4, the door 108 opens by rotating around an axis through thehinges 126. As will be further discussed below, if structures attachedto the door 108 extend too far away from the door 108, the structuresmay impact or hit sides or other portions of the microsatellite when thedoor 108 opens. Therefore, FIG. 4 shows a dashed circular reference line122 that represents the distance from the hinges 126 that is equal tothe width W of the door 108.

The antenna feed 102 can be optimally located approximately at the focalpoint of the reflector 106. The focal length, f, of the reflector 106may be constrained or limited to certain ranges or values, so that thedoor 108 can open without the antenna feed 102 (or other structures)impacting or hitting portions of the microsatellite. Also, the antennafeed 102 can advantageously be disposed such that it does not contact,impact, or displace the first or second baffles 114, 120 or the primaryor secondary minors 112, 118, if the first or second baffles 114, 120are not used. The height of the first light baffle 114 can be adjustedto prevent more or less radiation to impinge on the image sensor.Reducing the size of the light baffle 114 can create more space for theantenna feed 102, but the level of stray radiation on the image sensormay increase accordingly. Therefore, it can be desirable to achieve abalance between decreasing the length of or eliminating the first lightbaffle 114 and increasing the desired focal length, f, of the antennareflector 106. Similarly, the second light baffle 120 can be eliminatedor altered depending on the desired focal length, f, of the antennareflector 106 and the desired level of stray light baffling.

In some implementations, for the door 108 to open or close withoutobstruction, the positions of the antenna feed 102 and the antenna feedsupport 104 may be constrained or limited by the reference line 122. Forexample, any structure attached to the door 108 that extends beyond thereference line 122 may contact the side (or other portion) of themicrosatellite 100 and/or may come into contact with the opening in themicrosatellite 100 as the door 108 opened or closed. Thus, in certainimplementations, the focal length, f, of the antenna reflector may beselected such that no obstruction occurs.

The reflector 106 can have a diameter, d, that allows the door 108 toopen or close in an unobstructed manner. The diameter, d, can beapproximately equal to the length of the door 108 or substantially equalto the diameter of the opening in the microsatellite 100. It also may bedesirable that the curvature of the reflector 106 not be sufficientlylarge that the antenna reflector 106 extends beyond the reference line122, for substantially the same reasons why the antenna feed 102 shouldnot extend beyond the reference line 122.

The gain of a reflector antenna system is generally proportional to theaperture of the antenna reflector 106. It may be desirable to increasethe diameter, d, of the antenna reflector 106 to be substantially thesame length as the door 108 or opening in the microsatellite 100 so thata high gain is achieved. For some reflectors, the focal length, f, isrelated to the diameter, d, and depth, h, through the equation:f=d²/16h. For some such reflectors, the focal ratio, f/d, can be relatedto θ₀, the opening angle from the focal point to the edge of thereflector 106, through the equation: f/d=1/(4 tan(θ₀/2)). Improving oroptimizing the gain of the antenna system can involve adjusting theparameters (e.g., f, d, h) within the given constraints provided by amicrosatellite of a certain size and configuration to achieve anacceptable gain and data transmission rate.

In some embodiments, the antenna feed 102 can be a square structurehaving a known radiation pattern. The focal length, f, of the reflector106 can be adjusted once the diameter, d, of the reflector has beenselected based on the size of the door 108 or opening. The focal length,f, and depth, h, can be advantageously adjusted such that the antennafeed 102 efficiently illuminates the surface of the reflector 106. Theratio f/d can be advantageously tuned to improve or optimize antennagain. The properties of the reflector 106 can be adjusted to match theradiation pattern of the antenna feed 102. For example, the diameter, d,focal length, f, and depth, h, of the reflector 106 can be adjusted suchthat the radiation pattern of the antenna feed 102 illuminates thereflector 106 according to a desired pattern, function, or model.

For example, in an imaging microsatellite having a volume envelope of 60cm×60 cm×80 cm, the diameter of the antenna reflector can be about 48 cmand the focal length can be about 24 cm, giving a focal ratio, f/d, ofabout 0.5. The distance from the top surface of the first light baffle114 to the antenna feed 102 can be about 0.6 cm when the microsatelliteis in a non-deployed state. When the microsatellite is in a deployedstate, the antenna system can be configured to provide a gain of about28 dBi and a data transmission rate between about 1 Mbit/s and 100Mbit/s at a communication frequency between about 8.0 GHz and 8.4 GHz.

An imaging microsatellite having an integrated reflector antennaaccording to some embodiments described herein can transmit data acrossone or more (e.g., three) communication channels between about 1 Mbit/sand 100 Mbit/s per channel within the frequency band of about 8.0 GHz to8.4 GHz. A ground-based communication system with a receiving antennahaving a diameter of around 2 m can be sufficient to communicate with animaging microsatellite having an antenna system according to someembodiments described herein.

Example Method of Deploying an Imaging Microsatellite

FIG. 5 is a flow chart of a method 200 of deploying an imagingmicrosatellite according to some embodiments. In operational block 202the door opens by disengaging a release mechanism. An antenna system canbe mounted to the interior side of the door and configured to notdisturb, impact, or displace the imaging system when the microsatelliteis in a non-deployed state. The antenna system can be configured to notcontact or impact the satellite body or other structure when the dooropens. The antenna system can be configured to improve or optimize thegain and data transmission rate of the antenna system by adjustingproperties of the antenna system such as, e.g., the diameter or focallength of the antenna reflector and/or the curvature of the antennareflector.

In operational block 206 the door rotates a sufficient amount such thatthe door and attached antenna system do not obstruct the field of viewof an imaging system disposed within the imaging microsatellite. One ormore spring hinges can be included on the microsatellite and attached tothe door such that they apply a torque or a force to the door to causeit to rotate from a closed position in which the opening door covers theopening to the microsatellite to an open position in which the openingis unobstructed by the door and the imaging system can image a field ofview through the door. The field of view can include portions of theEarth over which the microsatellite orbits after launch.

In operational block 208, the door can be substantially secured in anopen position using any appropriate method, such as spring hinges,locking mechanisms, magnets, electromagnets, friction, or anycombination of these. In the open position, the antenna system can bedirected toward the ground so that the microsatellite can communicateimages from the imaging system and any other data to a ground receivingstation.

The deployment method according to some embodiments, as describedherein, advantageously can be relatively simple and reliable due to thesimplicity of the mechanical systems involved and the relatively smallnumber of moving parts.

Example Method of Designing an Imaging Microsatellite

FIG. 6 is a flow diagram representing an example of a method 300 ofdesigning an imaging microsatellite with an integrated reflector antennasystem. In operational block 302 configuration parameters of amicrosatellite can be obtained. The microsatellite can be configured toconform to the ESPA envelope, or other launch vehicle standards. Theconfiguration parameters can include the design, layout, dimensions, andconfiguration of the microsatellite including the available interiorcavity space and opening through which an imaging system can view theEarth. The configuration parameters can also include the design, layout,dimensions, and configuration of the imaging system disposed within theinterior cavity of the microsatellite. For example, the imaging systemmay include a telescope. The imaging system configuration parameters caninclude information about the size and configuration of the telescope,its primary and secondary (or other) minors, the position of telescopesupports that secure the primary and secondary minors into a desiredimaging configuration, and so forth.

In operational block 304, properties of the antenna system can beadjusted such that the antenna system does not impact, contact, ordisplace the imaging system when the microsatellite is in a non-deployedstate in which the antenna system is enclosed within the microsatellite.Properties of the antenna system can include, for example, an apertureof the antenna system, an antenna reflector diameter, an antennareflector focal length, an antenna reflector depth or curvature, aposition or orientation of the antenna feed relative to the antennareflector, a type of antenna feed, an antenna reflector shape, aconfiguration of an antenna feed support, or any combination of these.The properties of the antenna system can be adjusted such that theantenna system does not contact or impact the body of themicrosatellite, portions of the imaging system, or other structures whenthe microsatellite is in the non-deployed state. Also, properties of theantenna system can be adjusted such that the antenna system does notcontact or impact the body of the microsatellite, portions of theimaging system, or other structures while the microsatellite transitionsfrom the non-deployed state to the deployed state as the door to whichthe antenna system is attached opens.

In operational block 306, properties of the antenna system can beadjusted to improve or optimize the gain and/or data transmission rate.An antenna reflector and antenna feed can be configured to achieve adesired diameter, d, depth, h, and/or focal length, f. Some or all ofthese parameters can be adjusted such that the radiation pattern of theantenna feed illuminates or matches the antenna reflector to achieve adesired gain, data transmission rate, link margin, or othercommunication characteristics of the antenna system. The antenna systemgain or data transmission rate can be improved or optimized within theconstraints imposed by the installed imaging system by adjusting thefocal length, f, diameter, d, and/or depth, h, of the antenna reflector.In some implementations, the antenna system gain or data transmissionrate can be improved or optimized while keeping the communicationfrequency of the antenna in a particular communication band (e.g., 8.0GHz and 8.4 GHz). For example, in antenna systems that include aparaboloid antenna reflector, improving or optimizing the gain and/ordata transmission rate can be accomplished by positioning the antennafeed at the focal point of the antenna reflector and adjusting the focalpoint of the antenna reflector such that, when the microsatellite is inthe non-deployed state, the focal point lies between the primary andsecondary mirrors of the imaging system. The ratio f/d can then beadjusted to match the antenna feed radiation pattern thereby improvingthe antenna system gain or data transmission rate.

The method of design as described herein can provide for acost-effective imaging microsatellite that may improve or optimize theantenna gain while permitting the antenna system to be stowed within themicrosatellite during launch and easily deployed when the microsatellitereaches orbit. For example, the antenna system can be configured to fitwithin the interior cavity of a microsatellite without disturbing theimaging system and configured to provide sufficient gain and datatransmission rates to transfer image and video data to a ground-basedcommunication station.

Additional Examples and Embodiments of Deployed and Non-DeployedMicrosatellites and Example Methods of Use

As described herein, examples of an imaging microsatellite can include amicrosatellite that comprises a microsatellite body having an interiorcavity and an opening in the body. The microsatellite body can have anenvelope less than about 125 cm by 125 cm by 175 cm or a mass less thanabout 500 kg. The microsatellite optionally can include an optical sealconfigured to substantially surround a periphery of the opening. Themicrosatellite can include a door attached to the microsatellite body.The door can comprise a substantially planar member having an interiorsurface and an exterior surface. The interior surface of the dooroptionally can be configured to contact the optical seal when the dooris in a closed state. The microsatellite can include one or more hingesconnecting the door to the microsatellite body. The microsatellite caninclude an antenna system that comprises an antenna reflector attachedto the interior surface of the door, an antenna feed support attached tothe antenna reflector or interior surface of the door, and an antennafeed attached to the antenna feed support. The antenna feed support canbe configured to secure the antenna feed in a substantially fixedposition relative to the antenna reflector. The microsatellite caninclude an imaging system disposed within the interior cavity of themicrosatellite body. The imaging system can be configured to image afield of view through the opening. The imaging system can include aprimary minor, a secondary minor, and a secondary mirror support. Thesecondary minor support can be configured to secure the secondary minorin a substantially fixed position relative to the primary mirror. Theantenna system can be configured to fit within the interior cavity ofthe microsatellite when the microsatellite is in a non-deployed statesuch that the antenna system does not contact or displace the imagingsystem. The antenna system can be configured to move with the door suchthat the door can transition from a closed state to an open state in anunobstructed manner when the microsatellite transitions from anon-deployed to a deployed state. The antenna system can be configuredto provide a gain greater than or equal to about 25 dBi when themicrosatellite is in a deployed state.

Examples of an imaging microsatellite in a deployed state can include amicrosatellite comprising a microsatellite body having an interiorcavity and an opening in the body. The microsatellite can include a doorattached to the microsatellite body, the door comprising an interiorsurface and an exterior surface. The door can be configured to besecured in an open position by an opening mechanism. The microsatellitecan include an antenna system attached to the door. The antenna systemcan comprise an antenna reflector attached to the interior surface ofthe door, an antenna feed support attached to the antenna reflector orinterior surface of the door, and an antenna feed attached to theantenna feed support. The antenna feed support can be configured tosecure the antenna feed in a substantially fixed position relative tothe antenna reflector. The microsatellite can include an imaging systemdisposed within the interior cavity of the microsatellite body. Theimaging system can be configured to image a field of view through theopening in the body. The imaging system can comprise a primary minor, asecondary mirror, and a secondary mirror support. The secondary mirrorsupport can be configured to secure the secondary minor in asubstantially fixed position relative to the primary minor. The antennasystem can be configured to provide a gain greater than or equal toabout 25 dBi.

Examples of an imaging microsatellite in a non-deployed state caninclude a microsatellite comprising a microsatellite body having aninterior cavity and an opening in the body. The microsatellite canoptionally include an optical seal. The microsatellite can include adoor attached to the microsatellite body. The door optionally can beconfigured to be in contact with the optical seal. The door can beconfigured to cover the opening in the microsatellite body. Themicrosatellite can include an antenna system comprising an antennareflector attached to the door, an antenna feed support attached to theantenna reflector, and an antenna feed attached to the antenna feedsupport. The antenna feed support can be configured to secure theantenna feed in a substantially fixed position relative to the antennareflector. The microsatellite can include an imaging system disposedwithin the interior cavity of the microsatellite. The imaging system caninclude a primary mirror, a secondary minor, and a secondary mirrorsupport. The secondary minor support can be configured to secure thesecondary minor in a substantially fixed position relative to theprimary minor. The antenna system can be configured to fit within theinterior cavity of the microsatellite body without contacting ordisplacing the imaging system.

Examples of a method of transitioning an imaging microsatellite, asdescribed herein, from a non-deployed state to a deployed state caninclude disengaging a release mechanism. The release mechanism can beconfigured to secure a door against a body of the microsatellite whenengaged. The method can include opening the door wherein the door caninclude an antenna system attached to an interior surface of the door.The method can include rotating the door such that the door and theintegrated reflector antenna do not obstruct a field of view of animaging system. The method can include securing the door in an openposition. The antenna system can be configured to be disposed within aninterior cavity of the microsatellite without contacting or displacingthe imaging system when the microsatellite is in a non-deployed state.

In some embodiments of the method, the antenna system can be configuredto not obstruct the movement of the door during the opening step. Therelease mechanism can be a frangible bolt configured to be released byfracturing or melting the bolt.

The imaging system can be a telescope, such as, for example, aCassegrain or Ritchey-Chretien telescope. The integrated reflectorantenna can comprise a paraboloid reflector antenna configured to have afocal length, diameter, and curvature such that a desired gain or datatransmission rate is provided by the antenna system. The antenna feedcan be disposed between the primary and secondary minors of theCassegrain telescope. A diameter of the paraboloid reflector antenna canbe less than or equal to about 120 cm or greater than or equal to about30 cm, or the ratio of the diameter of the reflector to a width of thedoor can be less than or equal to about 0.98 or greater than or equal toabout 0.5.

Explanations of Certain Terms

Envelope is a broad term and is to be given its ordinary and customarymeaning to a person of ordinary skill in the art, and includes, withoutlimitation, volume or dimension limitations imposed on satellites forinclusion in a launch vehicle. For example, ESPA defines an envelope ofless than or equal to about 90 cm×70 cm×60 cm. As another example, somedefinitions of small satellites include an envelope of less than orequal to about 125 cm×125 cm×175 cm, less than or equal to about 100cm×100 cm×150 cm, or less than or equal to about 80 cm×60 cm×60 cm.

Reflector antenna is a broad term and is to be given its ordinary andcustomary meaning to a person of ordinary skill in the art, andincludes, without limitation, any reflector antenna with a surfaceconfigured to reflect electromagnetic radiation and substantiallyredirect it on a desired surface or other antenna element. For example,a parabolic reflector antenna may comprise a paraboloid surfaceconfigured to substantially focus incoming collimated radiation onto anantenna feed located at the focus of the paraboloid. Hyperboloidal orother shaped antenna reflectors can be used.

Antenna feed is a broad term and is to be given its ordinary andcustomary meaning to a person of ordinary skill in the art, andincludes, without limitation, an element that emits electromagneticradiation onto an antenna reflector, an element that absorbselectromagnetic radiation reflected from an antenna reflector, or both.An antenna feed can be, for example, a feed horn, a dipole drivenelement, waveguide, orthomode transducer, polarizer, and/or anycombination of these.

Link margin is a broad term and is to be given its ordinary andcustomary meaning to a person of ordinary skill in the art, andincludes, without limitation, the difference between the received powerand the receiver sensitivity in a communication system. Link margin,gain, noise, and bandwidth are all related to the rate at whichinformation can be transmitted across a communication system. Forexample, as the bit energy per noise density increases, the bit errorrate decreases, meaning that increasing the gain and bandwidth whilereducing the noise can increase the rate at which data may betransmitted.

Imaging system is a broad term and is to be given its ordinary andcustomary meaning to a person of ordinary skill in the art, andincludes, without limitation, lenses, minors, diffraction gratings,prisms, image sensors, optical systems, optical payloads, supportstructures, light guides, and/or any combination of these which make upa system that focuses and captures an image. An image may comprise pixeldata based on photons within a narrow frequency spectrum, a broadfrequency spectrum, multiple frequency spectrums, or any combination ofthese. An imaging system may capture single images or video at variousframe rates. An imaging system may be sensitive to photons within thevisible spectrum, infrared radiation, ultraviolet radiation, x-rays,gamma rays, microwaves, radio waves, or any combination of these.

SUMMARY

Examples of a microsatellite, integrated antenna, and imaging componentshave been described with reference to the figures. The components withinthe figures are not necessarily to scale, with emphasis instead beingplaced upon clearly illustrating the principles of how to incorporate asuitable integrated reflector antenna into an imaging microsatellite.The examples and figures are intended to illustrate and not to limit thescope of the inventions described herein. For example, the principlesdisclosed herein may be applied to satellites not classified asmicrosatellites such as, e.g., large satellites, small satellites,mini-satellites, and so forth.

Although certain preferred embodiments and examples are disclosedherein, inventive subject matter extends beyond the specificallydisclosed embodiments to other alternative embodiments and/or uses, andto modifications and equivalents thereof. Thus, the scope of the claimsappended hereto is not limited by any of the particular embodimentsdescribed herein. For example, in any method or process disclosedherein, the acts or operations of the method or process can be performedin any suitable sequence and are not necessarily limited to anyparticular disclosed sequence. Various operations can be described asmultiple discrete operations in turn, in a manner that can be helpful inunderstanding certain embodiments; however, the order of descriptionshould not be construed to imply that these operations are orderdependent. Additionally, the structures described herein can be embodiedas integrated components or as separate components. For purposes ofcomparing various embodiments, certain aspects and advantages of theseembodiments are described. Not necessarily all such aspects oradvantages are achieved by any particular embodiment. Thus, for example,various embodiments can be carried out in a manner that achieves oroptimizes one advantage or group of advantages as taught herein withoutnecessarily achieving other aspects or advantages as can also be taughtor suggested herein.

Conditional language used herein, such as, among others, “can,” “could,”“might,” “may,” “e.g.,” and the like, unless specifically statedotherwise, or otherwise understood within the context as used, isgenerally intended to convey that certain embodiments include, whileother embodiments do not include, certain features, elements and/orstates. Thus, such conditional language is not generally intended toimply that features, elements and/or states are in any way required forone or more embodiments. As used herein, the terms “comprises,”“comprising,” “includes,” “including,” “has,” “having” or any othervariation thereof, are intended to cover a non-exclusive inclusion. Forexample, a process, method, article, or apparatus that comprises a listof elements is not necessarily limited to only those elements but mayinclude other elements not expressly listed or inherent to such process,method, article, or apparatus. Also, the term “or” is used in itsinclusive sense (and not in its exclusive sense) so that when used, forexample, to connect a list of elements, the term “or” means one, some,or all of the elements in the list. Conjunctive language such as thephrase “at least one of X, Y and Z,” unless specifically statedotherwise, is otherwise understood with the context as used in generalto convey that an item, term, etc. may be either X, Y or Z. Thus, suchconjunctive language is not generally intended to imply that certainembodiments require at least one of X, at least one of Y and at leastone of Z each to be present.

It should be emphasized that many variations and modifications may bemade to the above-described embodiments, the elements of which are to beunderstood as being among other acceptable examples. All suchmodifications and variations are intended to be included herein withinthe scope of this disclosure and protected by the following claims.Further, nothing in the foregoing disclosure is intended to imply thatany particular component, characteristic or process step is necessary oressential.

What is claimed is:
 1. An imaging satellite comprising: a body having anopening; an imaging system disposed within the body; a door attached tothe body, the imaging satellite configured to have: a non-deployed statein which the opening is covered by the door, and a deployed state inwhich the opening is not covered by the door, the opening configured toallow radiation to enter the imaging system such that the imaging systemcan image a field of view through the opening; and an antenna systemmounted to an interior surface of the door, wherein the imagingsatellite is configured such that: when the imaging satellite is in thenon-deployed state, the antenna system is configured to not displace theimaging system, while the imaging satellite transitions from thenon-deployed state to the deployed state, the antenna system isconfigured not to contact the body of the imaging satellite, and whenthe imaging satellite is in the deployed state, the antenna system isconfigured to transmit imaging data acquired by the imaging system. 2.The imaging satellite of claim 1, wherein the imaging satellite has avolume that is less than or equal to 125 cm by 125 cm by 175 cm.
 3. Theimaging satellite of claim 1, wherein the imaging satellite has a massthat is less than or equal to 500 kg.
 4. The imaging satellite of claim1, wherein the imaging satellite has a mass that is in a range between 1kg and 10 kg.
 5. The imaging satellite of claim 1, wherein the imagingsatellite is configured to launch as a secondary payload on a launchvehicle configured to launch a primary payload.
 6. The imaging satelliteof claim 1 wherein the imaging system comprises a telescope comprising:a primary mirror; a secondary mirror; and a secondary mirror supportconfigured to secure the secondary mirror relative to the primary minor.7. The imaging satellite of claim 6, wherein the imaging system furthercomprises: a primary baffle associated with the primary mirror; or asecondary baffle associated with the secondary mirror.
 8. The imagingsatellite of claim 1, further comprising a release mechanism configuredto secure the door to the body when the door is in the closed state, therelease mechanism actuatable to release the door and allow the door tomove from the closed state to the open state.
 9. The imaging satelliteof claim 8, wherein the release mechanism comprises a spring.
 10. Theimaging satellite of claim 1, further comprising one or more solarpanels configured to provide power to electrical components in theimaging satellite.
 11. The imaging satellite of claim 1, wherein theantenna system comprises one or more of a feed horn, a dipole drivenelement, a waveguide, an orthomode transducer, or a polarizer.
 12. Animaging satellite comprising: a movable door configured to: cover aradiation entrance to the imaging satellite when the movable door is ina closed position; and uncover the radiation entrance to the imagingsatellite when the movable door is in an open position; an imagingsystem disposed in the imaging satellite, the imaging system configuredto receive radiation through the radiation entrance when the movabledoor is in the open position; and an antenna system coupled to an innersurface of the movable door, wherein the imaging satellite is configuredsuch that while the movable door moves from the closed position to theopen position, the antenna system does not contact or displace anyportion of the imaging system.
 13. The imaging satellite of claim 12,wherein the imaging satellite has a volume that is less than or equal to125 cm by 125 cm by 175 cm or a mass that is less than or equal to 500kg.
 14. The imaging satellite of claim 12, wherein the imaging satelliteis configured to launch as a secondary payload on a launch vehicleconfigured to launch a primary payload.
 15. The imaging satellite ofclaim 12 wherein the imaging system comprises a telescope that comprisesa primary minor and a secondary minor.
 16. The imaging satellite ofclaim 12, further comprising an opening mechanism configured to move thedoor from the closed position to the open position when the openingmechanism is actuated.
 17. The imaging satellite of claim 16, whereinthe opening mechanism comprises a spring.
 18. The imaging satellite ofclaim 12, further comprising one or more solar panels configured toprovide power to electrical components in the imaging satellite.
 19. Theimaging satellite of claim 12, wherein the antenna system is configuredto transmit imaging data acquired by the imaging system when the door isin the open position.
 20. The imaging satellite of claim 12, wherein theantenna system comprises one or more of a feed horn, a dipole drivenelement, a waveguide, an orthomode transducer, or a polarizer.